复杂构型前缘疏导热防护技术
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摘要
针对前缘驻点区热流密度高、热流梯度大的特点,基于疏导式热防护思想,研制了一体化疏导式热防护前缘结构.根据力热承载要求,设计了一体化薄壁结构方案,内部充装碱金属工质,在气动加热条件下形成工质相变及输运的热管式闭式循环,实现驻点区热量的快速疏散.通过结构封装、热管充装等工艺流程,实现结构样件,最终通过了飞行试验验证.结果表明,疏导结构启动时间约为94.5 s,疏导效率达到23.4%.
Based on dredging thermal protection method, an integrated leading edge structure was proposed to accommodate the severe heat flux and high heat flux gradient at the stagnation point. Considering the heat and force loadings, a thin shell structure with internal working medium was designed. Under thermal heating conditions, phase change and circulation of the working medium were established to achieve rapid heating transportation for the stagnation zone. The structure was integrated and then charged with working medium, and finally verified in flight test. The results showed that it started at about 94.5 s, and the thermal dredging efficiency achieved 23.4%.
Based on dredging thermal protection method, an integrated leading edge structure was proposed to accommodate the severe heat flux and high heat flux gradient at the stagnation point. Considering the heat and force loadings, a thin shell structure with internal working medium was designed. Under thermal heating conditions, phase change and circulation of the working medium were established to achieve rapid heating transportation for the stagnation zone. The structure was integrated and then charged with working medium, and finally verified in flight test. The results showed that it started at about 94.5 s, and the thermal dredging efficiency achieved 23.4%.
引文
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[13]Lu Q,Han H T,Hu L F,et al.Preparation and testing of nickel-based superalloy/sodium heat pipes[J].Heat and Mass Transfer,2017,53(11):3391-3397.
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[15]李同起,胡子君.定向高导热碳材料及其热管理结构设计[J].宇航材料工艺,2007,37(1):16-18,22.Li T Q,Hu Z J.Carbon materials with high directional thermal conductivity and their structure design of thermal management system[J].Aerospace Materials&Technology,2007,37(1):16-18,22(in Chinese).
[16]吴国庭.统一热管理的疏导式防热系统概念研究[J].航天器工程,2009,18(4):13-19.Wu G T.Conceptual research of leading thermal protection system with unified heat management[J].Spacecraft Engineering,2009,18(4):13-19(in Chinese).
[17]孙健,刘伟强.疏导式结构在头锥热防护中的应用[J].物理学报,2012,61(17):174401.Sun J,Liu W Q.Application of leading structure on thermal protection of nosetip[J].Acta Physica Sinica,2012,61(17):174401(in Chinese).
[18]孙健,刘伟强.尖化前缘高导热材料防热分析[J].航空学报,2011,32(9):1622-1628.Sun J,Liu W Q.Analysis of sharp leading-edge thermal protection of high thermal conductivity materials[J].Acta Aeronautica ET Astronautica Sinica,2011,32(9):1622-1628(in Chinese).
[19]刘冬欢,郑小平,王飞,等.内置高温热管C/C复合材料热防护结构热力耦合机制[J].复合材料学报,2010,27(3):43-49.Liu D H,Zheng X P,Wang F,et al.Mechanism of thermomechanical coupling of high temperature heat pipe cooled C/C composite material thermal protection structure[J].Acta Materiae Compositae Sinica,2010,27(3):43-49(in Chinese).
[2]Glass D E.Heat-pipe-cooled leading edges for hypersonic Vehicles[R].NASA 20080014285,2006.
[3]Colwell G T.Cooling hypersonic vehicle structures[C].Proceedings of 7thInternational Heat pipe Conference,Minsk,1990.
[4]李锋,艾邦成,姜贵庆.一种热平衡等温机制的新型热防护及相关技术[J].宇航学报,2013,34(12):1644-1650.Li F,Ai B C,Jiang G Q.A new thermal protection technology based on heat-balance isothermal mechanism[J].Journal of Astronautics,2013,34(12):1644-1650(in Chinese).
[5]李锋,等.疏导式热防护[M].北京:中国宇航出版社,2017.Li F,et al.Dredging thermal protection structures[M].Beijing:China Aerospace Press,2017(in Chinese).
[6]杨亚政,李松年,杨嘉陵.高超音速飞行器及其关键技术简论[J].力学进展,2007,37(4):537-550.Yang Y Z,Li S N,Yang J L.A review on hypersonic vehicles and key technologies[J].Advances in Mechanics,2007,37(4):537-550(in Chinese).
[7]Boman B,Elias T.Tests of a Sodium/Hastelloy X wing leading edge heat pipe for hypersonic vehicles[C].AIAA/ASME 5thJoint Thermophysics and Heat Transfer Conference,Seattle:1990.
[8]Glass D E,Camarda C J,Merrigan M A,et al.Fabrication and testing of Mo-Re heat pipes embedded in carbon/carbon[J].Journal of Spacecraft and Rockets,1999,36(1):79-86.
[9]Kasen S D.Thermal management at hypersonic leading edges[D].Charlottesville:University of Virginia,2013.
[10]姜贵庆.疏导式热防护若干问题的探讨[C].北京:飞行器热环境与热防护研讨会,2006:5.Jiang G Q.Research on dredging thermal protection[C].Beijing:Symposium on Thermal Environments and Thermal Protection Structures,2006:5(in Chinese).
[11]姜贵庆,艾邦成,俞继军,等.高温热管在疏导热防护技术中的应用[C].威海:第十一届全国热管会议论文集,2008:72-78.Jiang G Q,Ai B C,Yu J J,et al.Application of high temperature heat pipe in leading thermal protections[C].Weihai:Proceedings of 11thChina Heat pipe Conference,2008:72-78(in Chinese).
[12]Ai B C,Chen S Y,Yu J J,et al.Fabrication of Lithium/C-103 alloy heat pipes for sharp leading edge cooling[J].Heat and Mass Transfer,2018,54(5):1359-1366.
[13]Lu Q,Han H T,Hu L F,et al.Preparation and testing of nickel-based superalloy/sodium heat pipes[J].Heat and Mass Transfer,2017,53(11):3391-3397.
[14]韩海涛,邓代英,陈思员,等.尖前缘一体化高温热管结构设计与分析[J].机械强度,2013,35(1):48-52.Han H T,Deng D Y,Chen S Y,et al.Design and structural analysis of sharp leading edge integrated with heat pipe[J].Journal of Mechanical Strength,2013,35(1):48-52(in Chinese).
[15]李同起,胡子君.定向高导热碳材料及其热管理结构设计[J].宇航材料工艺,2007,37(1):16-18,22.Li T Q,Hu Z J.Carbon materials with high directional thermal conductivity and their structure design of thermal management system[J].Aerospace Materials&Technology,2007,37(1):16-18,22(in Chinese).
[16]吴国庭.统一热管理的疏导式防热系统概念研究[J].航天器工程,2009,18(4):13-19.Wu G T.Conceptual research of leading thermal protection system with unified heat management[J].Spacecraft Engineering,2009,18(4):13-19(in Chinese).
[17]孙健,刘伟强.疏导式结构在头锥热防护中的应用[J].物理学报,2012,61(17):174401.Sun J,Liu W Q.Application of leading structure on thermal protection of nosetip[J].Acta Physica Sinica,2012,61(17):174401(in Chinese).
[18]孙健,刘伟强.尖化前缘高导热材料防热分析[J].航空学报,2011,32(9):1622-1628.Sun J,Liu W Q.Analysis of sharp leading-edge thermal protection of high thermal conductivity materials[J].Acta Aeronautica ET Astronautica Sinica,2011,32(9):1622-1628(in Chinese).
[19]刘冬欢,郑小平,王飞,等.内置高温热管C/C复合材料热防护结构热力耦合机制[J].复合材料学报,2010,27(3):43-49.Liu D H,Zheng X P,Wang F,et al.Mechanism of thermomechanical coupling of high temperature heat pipe cooled C/C composite material thermal protection structure[J].Acta Materiae Compositae Sinica,2010,27(3):43-49(in Chinese).